| Nonlinear Equations of Motion for a Panel Subject to External Loads |
NOV 93 |
45 pages |
| Authors:
Mark A. Hopkins; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
 | The equations of motion of a constant thickness, rectangular panel subject to external static loads and unsteady supersonic aerodynamic forces is derived. Both isotropic and orthotropic panels are examined. The static loads come from in-plane forces, a temperature differential, and a pressure differential. The equations allow for slight initial curvature due to manufacturing imperfections. The equations are derived using a nonlinear strain- displacement relationship which permits both linear and nonlinear ... |
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| Robust Control Design with Real-Parameter Uncertainty and Unmodeled Dynamics. |
NOV 1990 |
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| Authors:
H. H. Yeh; S. S. Banda; S. A. Heise; A. C. Bartlett; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| Multidisciplinary Expert-Aided Analysis and Design (Mead). |
15 DEC 1989 |
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| Authors:
T. C. Hummel; J. Taylor; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
 | The MEAD Computer Program (MCP) is being developed under the Multidisciplinary Expert-Aided Analysis and Design (MEAD) Project as a CAD environment in which integrated flight, propulsion, and structural control systems can be designed and analyzed. The MCP has several embedded computer-aided control engineering (CACE) packages, a user interface (UI), a supervisor, a data-base manager (DBM), and an expert system (ES). The supervisor monitors and coordinates the operation of the CACE ... |
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| OPERATION DOMINIC. FISH BOWL SERIES. Project Officer's Report. Project 8A.3. Close-In Thermal and X-Ray Vulnerability Measurements--Shots Blue Gill and King Fish, |
01 SEP 1985 |
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| Authors:
F. D. Adams; O. R. Anderson; M. Annis; L. E. Ashley; M. P. Berardi; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| Aircraft Flight Performance Methods. Revision 2 |
JUL 85 |
284 pages |
| Authors:
L. E. Miller; P. G. Koch; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| This report addresses the problems associated with the derivation of aircraft performance characteristics. The emphasis is on segments which are a part of a mission profile. In particular, the following areas are studied; takeoff, climb, cruise, descent and glide, turning, and landing. The generalized approach to performance estimates is first presented. Next, appropriate solutions are derived. Last sensitivity relationships are developed. The relationships determine changes in the performance characteristics as ... |
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| Nonconservative Evaluation of Uniform Stability Margins of Multivariable Feedback Systems. |
APR 1985 |
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| Authors:
H. H. Yeh; B. Ridgely; S. Banda; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| This paper discusses concepts of stability margins of multivariable feedback systems. Independent and uniform stability margins are defined. A previous conjecture that the uniform margins may be computed by using the eigenvalue magnitudes instead of the singular values in the robust stability criteria is theorized. The nonconservatism provided by this theory in the evaluation of uniform margins is discussed, along with limitations of the uniform margins. Also presented is a ... |
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| Decoupling of High-Gain Multivariable Tracking Systems. |
FEB 1985 |
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| Authors:
D. B. Ridgely; S. S. Banda; J. J. D'Azzo; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| The problem of achieving a control system design that produces the tracking of command inputs and the decoupling of outputs of high-gain multivariable control systems is considered. The tracking requirements and the conditions under which the decoupling of outputs is possible are given. A procedure for selecting the design parameters is described. A new synthesis procedure for decoupling is described. The procedure is illustrated through numerical examples for several fighter ... |
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| Expert Systems in Maintenance Diagnostics for Self-Repair of Digital Flight Control Systems, |
JUN 1984 |
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| Authors:
J. Davison; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| This article covers three basic components of this program. One is an overview and the progress of the program starting off with the battle damage statistics that are supplied to us by aircraft battle damage repair people. These statistics are the drivers that influence the self-repairing program. These are gathered primarily from Southeast Asian data, updated from the Falklands conflict and Israeli data. Secondly, the article discusses briefly about the ... |
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| Design and Robustness Analysis of Reduced Order Controllers for Large Flexible Space Vehicles, |
JAN 1984 |
|
| Authors:
S. S. Banda; D. B. Ridgely; H. H. Yeh; D. V. Palmer; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| In the control design of a large flexible space vehicle, a finite element model is truncated and the control system is designed on the basis of the reduced order model. This paper discusses the step - by - step application of frequency-shaped Linear - Quadratic - Gaussian methodology, as well as payoffs and cost of this method. The procedure for choosing and forming both state and control frequency - weightings ... |
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| Aircraft Equipment Random Vibration Test Criteria Based on Vibrations Induced by Turbulent Airflow Across Aircraft External Surfaces |
1983 |
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| Authors:
John F. Dreher; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| Vibrations within jet aircraft are caused by a number of phenomena. The principal sources, generally are: jet engine noise and turbulent airflow (pseudo-noise) which impinge on aircraft external surfaces; gust, landing, and takeoff loads; and on-board mechanical equipment such as engines and pumps. This paper describes the structural vibrations induced by turbulent airflow and generalizes the findings to develop pertinent, adaptable random vibration test criteria for aircraft equipment. These criteria ... |
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| Technological Advances in Airframe-Propulsion Integration, |
JUN 1982 |
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| Authors:
D. Zonars; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| F-111A aircraft inlet system and TF-30 engine compatibility is reviewed based on an assessment of time averaged and instantaneous distortion parameters. In addition, recent advances in research on inlet configurations associated with steady-state and dynamic distortions are presented. A complete random data acquisition, editing and processing method is described for accomplishing data analysis as an inlet flow diagnostic tool. Finally, recent afterbody and nozzle research results, which improve the technology ... |
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| Boundary-Layer Transition on Blunt, Slender Cones at Hypersonic Mach Numbers, |
JUN 1982 |
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| Authors:
Kenneth F. Stetson; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| New wind tunnel data has been obtained to investigate the effects of tip bluntness and angle of attack on boundary layer transition on slender cones. The rearward displacement of transition due to tip bluntness and the maximum displacement of transition are reasonably well understood and explainable primarily on the basis of a reduction in local Reynolds number due to pressure losses across the bow shock. The rapid forward movement of ... |
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| Degradation of a Laser Beam by a Turbulent Jet, |
JUN 1982 |
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| Authors:
G. F. Cudahy; J. T. Van Kuren; H. E. Wright; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| A laser beam traversing turbulence undergoes an intensity reduction which is correlated with the statistical behavior of refractive index perturbations. The analytical relation predicts degradation as a function of beam diameter, path length, wave number and wave structure function. Refractive index perturbations are approximated via the equations of state using temperature and velocity perturbations. An experiment was conducted in which visible wavelength lasers traversed a well documented two-dimensional jet. Temperature ... |
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| Highlights of an Ejector Analysis, |
JUN 1982 |
|
| Authors:
Siegfried Hasinger; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| Ejectors are fluid energy transfer devices which rely on direct fluid momentum exchange in a mixing process. This direct exchange is responsible for the mechanical simplicity of ejector devices. This simplicity is, however, not shared by the analysis of these devices. The great number of variables which are of interest for ejector operations lead to considerable functional complexities. In addition the influence of some of the variables on the ejector ... |
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| Statistical Experimental Designs in Computer Aided Optimal Aircraft Design, |
JUN 1982 |
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| Authors:
K. S. Nagaraja; Ram B. Ram; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| A review of the statistical experimental designs which are relevant to the selection process of the design variables is made. Although several aerospace industries still use Latin Space techniques, the inherent shortcomings of the approach are not recognized. Optimal aircraft designs which are derived from such a deficient method become suspect, and reliability and cost saving can both become unattainable. An alternate approach, called D-optimal design, which has several advantages ... |
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| The Numerical Solution of Pressure Oscillations in an Open Cavity |
Jun-1982 |
35 pages |
| Authors:
W L Hankey; J S Shang; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Open cavities on aircraft exposed to high speed flow, such as bomb bays can give rise to intense self-induced pressure oscillations. The amplitude of these oscillations, under certain flight conditions, can cause structural damage. Substantial experimental and analytical efforts have investigated these pressure fluctuations, resulting in some understanding of the complex interaction of the external shear layer and cavity acoustical disturbances. However, no numerical computations have been obtained for the ... |
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| Pilot Models for Flight Control Analysis, |
MAY 1982 |
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| Authors:
R. O. Anderson; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| After a brief definition of pilot models, the two most common models (classical and optimal) are briefly described. The basic limitations and advantages of each are summarized. Next, some of the potential uses of these models are discussed along with a few non-aircraft oriented applications. The available data base to confirm models is reviewed and it is concluded that despite many very successful applications to date, overall understanding, use, and ... |
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| Reflections on the Effects of Vehicle Dynamics and Task Difficulty on Cooper-Harper Pilot Opinion Ratings Task Performance, and Pilot Workload, |
MAY 1982 |
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| Authors:
Robert B. Crombie; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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| This paper is intended to set forth generalized principles on a broad subject which lies at the heart of both flying qualities and human factors research, development, test, and evaluation. These generalizations are the result of the author's study of the flying qualities, pilot workload, and pilot performance literature. They are submitted to the participants of the Workshop on Flight Testing to Identify Pilot Workload and Pilot Dynamics to stimulate ... |
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| Automated Aircraft and Flight Control System Design, |
MAY 1982 |
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| Authors:
Morris A. Ostgaard; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| The following will discuss some of the characteristics of the human operator and their similarity to guidance and control functions. The operator's characteristics as a controller depend on four kinds of variables: control task variables, which include the system inputs and all the system elements external to the vibration, etc.; operator-centered variables such as training, fatigue motivation; and procedural variables such as instructions, practice, order of presentation relating to a ... |
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| Cockpit Design for the Future and Challenges to Workload Measurement, |
MAY 1982 |
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| Authors:
Larry C. Butterbaugh; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Workload assessment appears to have a major role to play both in the design of future cockpits, and in its application as a component of the crew system. the challenge to the development of workload measures and predictors is the need for sensitive, diagnostic techniques in the design process, and quantifiable, criterional measures for use in the flight-test and operational environments. |
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| Relationship of the Flying Qualities Specification to Task Performance, |
MAY 1982 |
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| Authors:
Frank L. George; David J. Moorhouse; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| It is recognized, that mission requirements will play an even greater role in future military aircraft design. As these requirements become more stringent, the effective integration of aerodynamics, performance and control will be essential to meeting them. Specification of open loop airplane characteristics based on implied or indirect closed loop requirements will not be adequate. It appears knowledge of the pilot's dynamic and performance characteristics is necessary to quantitatively relate ... |
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| The AFTI/F (Advanced Fighter Technology) Flight Test Program and Opportunities to Evaluate Pilot-Vehicle Interface and Mission Effectiveness, |
MAY 1982 |
|
| Authors:
Robert B. Crombie; Michael L. Frazier; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| The AFTI/F-16 flight test program will offer many opportunities for the Air Force, NASA, and Navy to evaluate pilot-vehicle interface and mission effectiveness. The AFTI/F-16 vehicle contains an advanced systems capability that will enhance the pilots ability to control the aircraft. Automated modes will configure these systems to help the pilot and vehicle to better perform realistic combat mission tasks. The first year's flight test plan has many pilot-in-the-loop maneuvers ... |
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| Large-Amplitude Multimode Response of Clamped Rectangular Panels to Acoustic Excitation |
09 SEP 1981 |
29 pages |
| Authors:
Mei Chuh; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| A mathematical formulation and the solution procedure for rectangular panels under broadband random acoustic excitation are presented. Large-amplitude effect and multiple modes are included in the formulation. The generalized mass matrix and the generalized linear stiffness matrix using 15 terms in the assumed panel deflection function are derived. Subroutine programs that generate the mass and linear stiffness matrices have been developed. Continuing research efforts are outlined. ... |
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| Skin Friction Measurements at a Mach Number of Three and Momentum Thickness Reynolds Numbers Up to a Half Million. |
SEP 1980 |
|
| Authors:
Anthony W. Fiore; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Surface shear stress measurements were made in the Flight Dynamics Laboratory's M=3 High Reynolds Number wind tunnel. The primary purpose of this research was to make shear stress measurements at very high Reynolds numbers for near adiabatic wall and zero pressure gradient conditions. The results are presented as the local skin friction coefficient versus both the momentum thickness and the length Reynolds number. The investigation was conducted on the nozzle ... |
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| Computer Simulation of Ejection Seat Performance and Preliminary Correlation with Empirical Data. |
APR 1980 |
|
| Authors:
Lanny A. Jines; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| The comparison of six-degree-of-freedom computer program modeling ejection seat performance to empirical data from ejection seat track tests is discussed. The computer subroutines model the ejection seat components which generate forces on the seat and crewperson combination during ejection. The resulting motion described in terms of trajectory parameters, as well as acceleration time histories on the ejectee is correlated with measured data from recent Air Force track test programs in ... |
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| Evaluation of the Impact Computer Program as a Linear Design Tool for Bird-Resistant Aircraft Transparencies. |
MAR 1980 |
|
| Authors:
Robert E. McCarty; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| The use of a finite element structural analysis computer program called IMPACT to simulate the transient response of B-1 aircraft windshield panels to bird impact is discussed. For the two simulations accomplished, computed results were compared to experimental data acquired during bird impact tests of actual windshield panels. For the first case of a panel tested at ambient temperature the computed results were qualitatively accurate. Strain levels measured during the ... |
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| Research in Computational Aerodynamics. |
FEB 1980 |
|
| Authors:
W. L. Hankey; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Experience obtained by the Computational Aerodynamics Group, WPAFB, in numerically solving viscous flow problems with the Navier-Stokes equations shall be addressed. Topics discussed include grid generation for arbitrary geometries, numerical instabilities, turbulence models, accuracy, efficiency, and smearing of discontinuities. Applications are reported for the method to solve shock wave-boundary layer interactions, 3D interactions, inlets and nozzle flow fields and unsteady viscous flows. (Author) |
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| A Compilation of Computer Software Programs Available in the Flight Dynamics Laboratory, 1979 |
DEC 1979 |
|
| Authors:
James L. Terry; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| A compilation of computer programs useful in the analysis and design of aerospace vehicles. Technical areas covered include: aerodynamics; flight control; vehicle dynamics; crew escape; vehicle structures; vehicle subsystems (i.e. landing gear); preliminary design and analysis; mathematical aids to analysis. This report supersedes Air Force Flight Dynamics Laboratory Technical Report AFFDL-TR-74-26, 'A Library of Computer Programs in Flight Vehicle Technology, 1973.' |
|
| Suppression of Aerodynamically Induced Cavity Pressure Oscillations |
NOV 1979 |
62 pages |
| Authors:
Leonard L. Shaw; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| A flight test program was performed to gain further insight into the phenomenon of flow-induced cavity pressure oscillations and to evaluate the effectiveness of suppression concepts in eliminating or reducing the pressure oscillations. The cavities tested were rectangular with approximate dimensions of 17 inches long, 8.5 inches deep, and 8.75 inches wide and were instrumented with microphones, static pressure ports, and a thermocouple. The flight speeds ranged from Mach number ... |
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| Proceedings of the Annual Conference on Manual Control (15th) held March 20 - 22, 1979, Wright State University, Dayton, Ohio |
NOV 1979 |
|
| Authors:
Frank L. George; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Fifty-six papers were presented during this conference on Manual Control and all are represented, either as complete papers on as abstracts provided by the authors. Topics of the papers include higher order manual tasks involving attention allocation and decision-making, human dynamic modeling and identification, and design methodology for human operator controlled systems. Also covered were aspects of control manipulators and displays, as well as considerations for simulation of human operator-controlled ... |
|
| Transient Thermal Effects in Disc Brakes. |
NOV 1979 |
|
| Authors:
Ben J. Brookman Jr; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| An investigation was undertaken with the ultimate objective being to develop a general theoretical model for predicting temperatures within the stators, rotors, rim, torque tube, tire, fuse plug and bead seat of a typical disc brake assembly. The effort was divided into four phases: (1) Temperature Measurement Analysis, (2) Theoretical Analysis of Brake and Component Parts, (3) Full Scale Brake Tests, and (4) Correlation of Results. |
|
| Flying Qualities Design Requirements for Sidestick Controllers |
OCT 1979 |
186 pages |
| Authors:
G. Thomas Black; David J. Moorhouse; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Five flight test experiments using the variable stability NT-33A were sponsored by AFWAL/FIGC from May 1977 to June 1979, conducted by students of the Air Force Test Pilot School. This data has been correlated with previously published flying qualities information to form guidance on design of sidestick controllers. Preferred force and deflection gradients are indicated. There is an apparent influence of short-period frequency and roll mode time constant on the ... |
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| A Combined Environments Reliability Test (CERT) Facility for Testing of Airborne Equipment. |
SEP 1979 |
|
| Authors:
Harriman E. Reynolds; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| A third combined environment reliability test facility has been developed with improved capability to simulate the dynamic combined environments that internally carried aircraft equipment is exposed to in modern high performance military aircraft. An electro-pneumatic control system individually controls compartment temperature, humidity, air mass flow and altitude, and equipment cooling air temperature, humidity, and mass flow from a tape deck according to aircraft ground and flight profiles programmed on magnetic ... |
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| Recovery System Preliminary Design, a Simplified Approach to Determining Staging, Timing and Altitude Requirements for Fast Inflating Parachutes. |
SEP 1979 |
|
| Authors:
Michael W. Higgins; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Determining a recovery system design that will take a specified act of initial conditions and will operate within a given set of constraints to provide a required final condition is a complex task. To perform this task, current design practices make extensive use of both person hours and computer time in an analytical 'cut and try' process. This report documents an analytical technique that takes a specified set of inputs ... |
|
| Test Report on Vibration Measurements on the C-141 Laser Test |
AUG 1979 |
78 pages |
| Authors:
David L. Banaszak; Dansen Brown; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| This test report presents data which define the vibration environment of a chemical laser system on a C-141 aircraft. These data were needed to determine if there are any severe vibration problems due to the abnormally large amount of weight added by the laser system to the C-141 petal door area. |
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| Variations in Crack Growth Rate Behavior |
AUG 79 |
|
| Authors:
M. E. Artley; J. P. Gallagher; H. D. Stalnaker; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Three variable amplitude stress histories based on a single repeating flight of a bomber aircraft are applied to two 610 mm wide, 4.6 mm thick, center-crack panels of 7075-T6 aluminum. The stresses in each stress history are controlled so that the stress intensity factor coefficient (K/sigma) is maintained constant as the crack grows. The resulting fatigue crack growth (FCG) data are utilized to show that the derived variable amplitude fatigue ... |
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| Integration of Flight and Fire Control. |
AUG 1979 |
|
| Authors:
Robert R. Huber; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| This paper describes a US Air Force sponsored program to evaluate Integrated Flight and Fire Control (IFFC) systems in modern fighter aircraft. IFFC systems for air-to-air gunnery, air-to-ground gunnery, and bombing are outlined. The concept involves the coupling of fire control commands into the flight control system. The goals of the IFFC system are improved accuracy, expanded employment envelope, and increased survivability. The concept will be tested on a F-15B ... |
|
| Improved Programs to Transfer Data From a Nicolet 1090 Digital Oscilloscope to a Hewlett-Packard 9810 Calculator |
JUL 1979 |
25 pages |
| Authors:
David V. Breitenbecher; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| These two programs were written to transfer data from a Nicolet 1090 digital oscilloscope through a Hewlett-Packard 9810 calculator that stores the data on a specially prepared tape cassette. They were written to replace a series of six programs described in AFFDL-TM-77-20 and thus simplify the oscilloscope recording process. Also included are operating instructions for these programs. |
|
| Digital Computer Solution of Aircraft Longitudinal and Lateral - Directional Dynamic Characteristics. |
JUL 1979 |
|
| Authors:
John M. Griffin ; Robert B. Yeager ; Larry B. Jordan ; David A. Ratino; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Two Fortran IV computer programs are presented for the solution of aircraft longitudinal and lateral-directional transfer function factors and dynamic characteristics. The longitudinal program solves for the three-degree-of-freedom dynamic characteristics (phugoid damping ratio and natural frequency, short period damping ratio and natural frequency, etc.) and the numerator factors of the alpha, u, theta, h, and vertical acceleration transfer functions. The lateral-directional program solves for the three-degree-of-freedom characteristics (Dutch roll damping ... |
|
| Investigation of a Deployable Polyurethane Foam Ground Impact Attenuation System for Aerospace Vehicles. Volume II. FIAS Test Numbers 49 through 91. |
JUL 1979 |
229 pages |
| Authors:
Stephen R. Mehaffie; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| An investigation was conducted to determine the feasibility of an advanced deployable impact attenuation system for use with aerospace vehicles. Performance of the system with a boilerplate AQM-34V RPV was quantified through a series of full-scale impact tests. A prototype design and costing analysis is presented. The conclusion was that the Foam Impact Attenuation System (FIAS) could provide the optimum system for the ground recovery of RPV's. (Author) |
|
| A Method for Assessing the Impact of Wake Vortices of USAF Operations |
JUL 1979 |
|
| Authors:
George Kurylowich; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| Experience as a consultant to the Safety Office at Norton AFB led to compiling the engineering tools presented so that this report can be used by engineering personnel to investigate future incidents/accidents and existing USAF operations that are impacted by the vortical wake hazard. The approach presented is amenable to easy hand computations. Mixed airplane/helicopter operations can be assessed, since the engineering tools to determine the location and strength of ... |
|
| The History of Static Test and Air Force Structures Testing |
JUN 1979 |
300 pages |
| Authors:
Bernard C. Boggs; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| This report traces the history of aircraft static testing from its early beginning and follows the development of structures testing in the United States Air Force from 1917 to 1979. Those technologies that are related to structures testing are included which were important to airplane structures strength. Test technology development which provided test facilities, tests systems and test methods are covered for the static, dynamic, fatigue, and environmental simulation of ... |
|
| The Analysis of Sound Propagation in Jet Engine Ducts Using the Finite Difference Method. |
JUN 1979 |
60 pages |
| Authors:
Dennis W. Quinn; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| In this report, the author derives the partial differential equations which describe sound propagation in jet engine ducts and then presents a finite difference approach for solving these equations. Also included is a computer program listing, sample input and sample output. The program can handle uniform rectangular and cylindrical ducts with or without uniform flow. In addition, if a mapping function which maps a nonuniform duct to a uniform duct ... |
|
| Facility Air Control Systems Design for a Pilot Transonic Wind Tunnel |
MAY 1979 |
56 pages |
| Authors:
Maurice R. Cain; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| In late 1973 and early 1974 plans were being formulated in the Air Force Flight Dynamics Laboratory (AFFDL) for constructing a wind tunnel with a fifty inch square test section with variable geometry walls. The variable geometry of the walls would provide an adaptive test section which would allow testing larger models in a smaller tunnel than possible in a comparable sized conventional tunnel. The ... |
|
| Investigation of Numerical Techniques for Predicting Aerodynamic Heating to Flight Vehicles |
MAY 1979 |
120 pages |
| Authors:
Arthur B. Lewis Jr; Neil J. Sliski; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| The development of complex lifting configurations and high speed maneuvering vehicles has emphasized the need for numerical techniques to predict aerodynamic heating rates as a function of the vehicle trajectory. These numerical programs are not expected to eliminate the requirements for wind tunnel and flight testing, but will be an aid to more efficient use of experimentation time and improve confidence that all potential problem areas on the vehicle have ... |
|
| Aerodynamic Heating in the Fin Interaction Region of Generalized Missile Shapes at Mach 6 (Modular Missile Test Program) |
MAY 1979 |
171 pages |
| Authors:
Richard D. Neumann; James R. Hayes; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| The characteristics of three-dimensional shock wave turbulent boundary layer interactions are investigated for a finned ogive-cylinder configuration. An extensive experimental program was conducted in the AEDC/VKF Tunnel 'B' at Mach 6 and a unit Reynolds number of 4.9 million per foot. The model was an ogive-cylinder 50 inches long and 8.5 inches in diameter with fins mounted at model station 42. Heat transfer data were taken on the cylinder and ... |
|
| Digital Load Control Applied to Full-Scale Airframe Fatigue Tests. |
MAY 1979 |
173 pages |
| Authors:
Nirmal K. Mondol; Richard M. Potter; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| The modeling, analysis and digital simulation of an analog servo controller and its successful application to a full-scale airframe fatigue tests is described. Primary emphasis is on the use of minicomputers for dynamic load control of multiple channels. Hardware and software used to generate functions and control load is described. A brief comparison of digital system performance versus conventional analog controllers is included. (Author) |
|
| Manufacturing Cost Data Collection and Analysis for Composite Production Hardware |
MAY 1979 |
109 pages |
| Authors:
B. I. Rachowitz; R. J. Coletti; A. J. Tornabe; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| This technical report documents the procedures used to validate the Advanced Composite Cost Estimating Model, by comparing the model output with actual costs measured during production fabrication. This validation also includes recommendations as to the limitations and improvements that can be made to the model. |
|
| Airflow Effects on Fires. Part II. |
MAY 1979 |
|
| Authors:
Thomas Weeks; Charles C. Gebhard; Gilbert L. Camburn; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| This report expands the knowledge of airflow effects on fuel fires initiated by nonnuclear combat damage obtained from previous work reported in JTCG/AS-T-75-001. An investigation is made into the influence of selected airflow parameters (coefficient of pressure and the bonudary layer thickness) upon the blowout velocity for a variety of damage conditions and angles-of-attack. (Author) |
|
| Skin and Spar Interface Program (SASIP). |
MAY 1979 |
|
| Authors:
Allen Gonsiska; Richard T. Achard; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
|
| This program had two basic goals. First was the investigation of the effects of fuel pressure (flatwise tension) loads and chordwise (transverse tension) loads on several integral composite skin/spar concepts. The second goal was the development of suitable tooling which could be used to produce these types of structural components. Several concepts were designed, produced, and tested under the required loading conditions. Results indicated that (a) integral composite skin/spar concepts ... |
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Reports by Corporate Author
